Multi-pierced combustion chamber with counter-rotating tangential flows
View Patent ↗A combustion chamber, for example for a turbine engine, presenting an inner annular wall, an outer annular wall, and a pierced annular chamber end wall extending around an axis, the chamber end wall including at least one opening receiving a fuel injector, the opening being substantially centered on a circular line defining a first chamber end wall portion extending radially between the circular line and the inner annular wall, and a second chamber end wall portion extending radially between the circular line and the outer annular wall. First and second channels are inclined relative to a normal vector normal to the chamber end wall while extending tangentially, the first channels arranged to provide a flow of air in a first rotary direction, the second channels arranged to provide a flow of air in a second rotary direction opposite to the first rotary direction.
1. A combustion chamber presenting an annular shape about an axis, comprising:
an inner annular wall, an outer annular wall, and an annular chamber end wall extending around the axis, the annular chamber end wall extending radially between the inner annular wall and the outer annular wall, the annular chamber end wall including at least one opening which receives a fuel injector, the at least one opening being centered on a circular line, the circular line defining a first chamber end wall portion extending radially between the circular line and the inner annular wall and a second chamber end wall portion extending radially between the circular line and the outer annular wall;
a plurality of first channels formed in the first chamber end wall portion and located radially between a radially innermost end of the at least one opening and the circular line; and
a plurality of second channels formed in the second chamber end wall portion and located radially between a radially outermost end of the at least one opening and the circular line,
wherein the annular chamber end wall is connected to upstream ends of the inner annular wall and the outer annular wall so as to extend radially between the upstream ends of the inner annular wall and the outer annular wall and continuously with the inner annular wall and the outer annular wall,
wherein the plurality of first channels and the plurality of second channels are inclined relative to a normal vector normal to the annular chamber end wall while extending tangentially, in a frame of reference (ur, uθ, Z) defined relative to the axis, ur being a radial axis, uθ being a circumferential axis, and Z being an axis parallel to the axis, a tangential direction is a direction parallel to the circumferential axis uθ,
wherein the radially innermost end of the at least one opening and the radially outermost end of the at least one opening lie on the radial axis,
wherein the plurality of first channels directs air to flow around the axis in a first rotary direction while the plurality of second channels directs air to flow around the axis in a second rotary direction opposite to the first rotary direction,
wherein a projection of each of the plurality of first channels and each of the plurality of second channels onto a plane orthogonal to the axis is tangential to a circle centered on the axis, and
wherein a radial width of the air flowing in the first rotary direction directed by the plurality of first channels is substantially equal to a radial width of the first chamber end wall portion extending radially between the circular line and the radially innermost end of the at least one opening, and a radial width of the air flowing in the second rotary direction directed by the plurality of second channels is substantially equal to a radial width of the second chamber end wall portion extending radially between the circular line and the radially outermost end of the at least one opening.
2. A combustion chamber according to claim 1 , further comprising at least one swirler co-operating with the at least one opening, the swirler generates a rotary air flow around the at least one opening in phase with the first and second rotary directions.
3. A combustion chamber according to claim 1 , further comprising a plurality of third channels formed in the first end wall portion, the plurality of third channels being inclined relative to the normal vector while extending radially.
4. A combustion chamber according to claim 3 , wherein the plurality of third channels provide a substantially centripetal radial flow of air.
5. A combustion chamber according to claim 3 , wherein the plurality of third channels are arranged in proximity of the inner annular wall.
6. A combustion chamber according to claim 5 , wherein the plurality of first channels and the plurality of second channels are inclined relative to the normal vector at an angle lying in a range of 10° to 400.
7. A combustion chamber according to claim 1 , further comprising a plurality of fourth channels provided in the second end wall portion, the plurality of fourth channels being inclined relative to the normal vector while extending radially.
8. A combustion chamber according to claim 7 , wherein the plurality of fourth channels provide a substantially centrifugal radial flow of air.
9. A combustion chamber according to claim 7 , wherein the plurality of fourth channels are arranged in proximity of the outer annular wall.
10. A combustion chamber according to claim 3 , further comprising a plurality of fourth channels provided in the second end wall portion, the plurality of fourth channels being inclined relative to the normal vector while extending radially.
11. An aircraft turbine engine, comprising a combustion chamber according to claim 1 .
12. A combustion chamber according to claim 5 , wherein the plurality of third channels are distributed over at least one annular row adjacent to the inner annular wall.
13. A combustion chamber according to claim 9 , wherein the plurality of fourth channels are distributed over at least one annular row adjacent to the outer annular wall.